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SpaceTech GmbH Company Presentation

2/2018

Company Profile

2018 Company Presentation 2

Facts & Figures Foundation: 2004

Staff: 100 (avg. age 39)

Yearly Turnover: 20 M€

Annual Growth: ~10%

Substantial Expansion in Progress

SpaceTech GmbH Seelbachstrasse 9-11-13

88090 Immenstaad

Germany

www.spacetech-i.com

International

Staff

Systems Mission Design

Small Satellites

Constellations

End-to-End Systems

Instruments

Optical Instruments

Ultra-Stable Instrument Structures & Mechanisms

Equipment Solar Generators

Structures & Mechanisms

Electronics

Instrument Equipment

Executive Board: Wolfgang Pitz (CEO), Frank Gilles, Bernhard Doll (Founder)

Company Heritage – onboard of 14 missions


Systems Mission Design

Small Satellites

Constellations

End-to-End Systems

Instruments

Optical Instruments

Ultra-Stable Instrument Structures & Mechanisms

Formosat-5 ICARUS M2Space

GRACE FO LRI MERLIN FRU LISA/NGGM Laser

Solar Generators GT2, FS5, S5P, Space IL, NGSAR,EUCLID,…

Structures GRACE FO, Formosat-5 BepiColombo,…

Mechanisms JUICE, Sentinel 6, GFO,GT2, FS5, S5P,…

Equipment Solar Generators

Structures & Mechanisms

Electronics

Instrument Equipment

Company Profile - Facilities

Company Presentation 4

Clean Rooms ISO 8 / class 100,000

ISO 7 / class 10,000

ISO 5 / class 100

Manufacturing Capabilities Electronic labs

Mechanical workshops

Laser-optics lab

Mechanical integration hall

Carbon Fibre production facility

Test Facilities Several thermal vacuum chambers

Temperature cabinets

Shakers and shock tables

2018

STI Site Extension Plan


2018: new building G4 for Solar Generator Factory, STI and CST Offices

2020+: new buildings G5 and G6 EV Tests and Cleanroom, STI and CST offices

Carbo-SpaceTech (CST)

12 000 m2 STI Site

2017: Present

SpaceTech Customers & Partners


Company Organization


SpaceTech develops small satellites, providing low cost solutions for a wide range of applications.

Formosat 5 “Satellite Kit”

Sys. Eng. Support, Procurement

Structure, solar generator, propulsion, sun sensor

Launched in 08/2017

DEOS Phase A prime, Phase B Client prime

Mission/satellite design

Design of the docking/berthing mechanism

Mission stopped by DLR after Phase B

ICARUS Tracking of animals from space

ISS payload, attached to Russian Module

Launch scheduled for October 2017

Small Satellites & Missions


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M2Space - Initiative


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Making M2M Communication Global The IoT market is large and growing fast from 20 B$ today to 75 B$ in 2025 (IHS Forecast).

Applications with demand for global connectivity are currently restricted by the reach of terrestrial networks, covering only 90% of the IoT market.

SpaceTech has started an initiative for the implementation of a satellite-based IoT Service:

M2Space Constellation Gen 1 / Tranche 1 until 2021: 4 Satellites - latency ~3 h (< 7h)

M2Space Constellation Gen 1 / Tranche 2 until 2023: 12 Satellites - latency ~ 1h (<2h)

M2Space Constellation Gen 2: 48 Satellites – communication in quasi-real-time

M2Space Unique Characteristics

Smallest Sensors with direct link to space

Interoperability with existing terrestrial IoT- Systems and Smartphones

Selectable channels for different Frequencies/Encoding

SpaceTech leading edge payload technology with heritage

Status

Consolidation Phase started with venture capital funding

Open for Anchor Customers/Channel Partners/Strategic Investors

Optical Instrument activities - overview

2018 Company Presentation

10

SpaceTech develops laser-optical systems with a focus on earth observation and science missions.

GRACE Follow-On Prime for German Laser Ranging Interferometer part

Cooperation with JPL/NASA

Ranging noise 80 nm/Hz

Launch scheduled for March 2018

MERLIN Frequency Reference Unit (FRU) German-French mission on methane gas measurement

Subsystem for absolute frequency reference

FM delivery in 2018

High Stability Laser (HSL) Laser system for NGGM, GRACE 2, LISA…

Fiber amplifier, reference cavity, control electronics

> 500 mW, frequency noise 40 Hz/Hz < 1 Hz

EBB completed, component qualification running

GWO Metrology Laser (BB, EM) Laser system for LISA, 2 W output power

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SpaceTech develops deployable solar generators, with focus on dedicated solutions for Earth observation and science missions.

GökTürk 2 Deployable solar array

Delivered in 2010

Launched in 2012

Formosat-5 Deployable mounted solar array

Delivered in 2012

Launched in August 2017

Sentinel-5 Precursor Deployable solar array

Delivered in 2014

Launch scheduled for 2017

In development (C/D contract) Space IL, delivery in 2017

NGSAR, delivery in 2017

C-Sat, delivery in 2017

EUCLID, delivery in 2018

JASON CS, delivery in 2019

Solar Generators


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Structures, Mechanisms & MGSE


Formosat-5 Primary structure, top panel, MGSE

Delivered in 2012/2013

Launched in August 2017

Bepi Colombo STM of MOSIF Sun Shield

Delivered in 2009


GRACE Follow-On Primary and secondary structure, MGSE

Deployable S-Band antenna boom

Delivered in 2015/2016


Refocus Mechanisms (BB tests completed) Motor driven (0.5 µm accuracy, 300 µm travel)

Heater driven (0.5 µm accuracy, 10 µm travel)

In development (C/D contract) JUICE RIME antenna

Sentinel-5 Calibration Subsystem (CAS)

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Deployment Mechanisms


STI develops reliable and robust deployment mechanisms, mainly as part of solar generator or antenna contracts.

Kompsat-3: Solar Array Spring driven cam system with high torque margin

CFRP strut with metal C-springs, low latching shock

GökTürk-2: Solar Array

Spring driven cam system with high torque margin

No strut, low deployed stiffness, low latching shock

Sentinel-5 Precursor: Solar Array Spring driven cam system with high torque margin

CFRP strut with metal C-springs, low latching shock

GRACE FO: Antenna Boom Spring driven cam system with high torque margin

Aluminum boom

Current developments (C/D contracts) JUICE RIME antenna (slotted CFRP, multi-hinge).

Boom is covered by silver strip to act as antenna.

Improved, adapted mechanisms for Jason-CS and C-Sat

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2018

AOCS Sensors


OSS on Formosat-5 Omnidirectional Sun Sensor (OSS)

Based on 6 orthogonally oriented solar cells

< 15° peak error

CESS Omnidirectional Coarse Earth and Sun Sensor

Based on 6 orthogonal oriented CESS heads

< 12° peak error on Earth vector

< 5° peak error on Sun vector

Supports spin rates up to 10°/s

2 FM sets delivered by STI, 7 FM sets under contract

Background/Heritage Flight heritage on over 15 LEO satellites

Patented by B. Doll & W. Pitz (when at Airbus)

STI has Airbus exclusive license

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Electronics


SpaceTech develops electronics with focus on: Power control and distribution units

Instrument control units

Ultra low noise current sources

GökTürk 2 Pyrodrive Module

Launched in 2012

Satellite Core Avionics (EM completed) Combination of OBC and PCDU for small satellites

Prototype demonstrated in 2015

MERLIN Frequency Reference Unit FRU control electronics, FPGA based

FM delivery scheduled for 2018

Laser diode drivers Ultra low noise current sources

For use with e.g. DFB & ECDL Lasers

BB ready, FM delivery scheduled for 2018

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RCSMTMT

3-axisGPSGPS

CESS /

OSS

AOCS Equipment

ThermHeater

Thermal Ctrl. Equip.

SCSCCESS /

OSSCESS

6 heads

AOCS SensorsAOCS ActuatorsHead

Head

RCSRCS

3 branches A, B, C

HeaterHeater ThermTherm

3 groups A, B, C

EGSESA Generator Battery S-Band RFEA

Cold/hot redundant

functional redundant

Satellite Core

Avionics

CAN-Bus B

Umbilical /

Test IF

SPC Module N

(SCOC3)

Pwr

POL

Pwr IF

CA int. PWR A

CA int. PWR B

CAN-Bus A

Ctrl B

Ctrl A

CAN A CAN B

SPC Module R(SCOC3)

CAN A CAN B

Pwr

POL

TX TXRX RX

TMTCTMTC

I/O Module A

RCS A

CESS A

SC A

MT A

Payload A

Heater A

Therm A

I/O Module B

RCS B

CESS B

SC B

GPS A

Payload B

Heater B

Therm B

I/O Module C

RCS C

CESS C

GPS B

MT B

Heater C

Therm C

Ctrl

CAN A CAN B

Ctrl

CAN A CAN B

Ctrl

CAN A CAN B

SC A, B GPS A, BCESS A, B, CHeater A, B, C Therm A, B, C MT A, B RCS A, B, C

CAN-bus

I/F =

CAN-bus or

UART or Spacewire

Primary Power

Int.Power to I/O

Modules 3x

Pwr

POL

Pwr

POL

Pwr

POL

Nominal Redundant

4xR

FE

A

3-6

x N

EA

2xG

PS

2x S

C

4xP

aylo

ad

Payload / Instrument

IF A IF BIF A IF B

DCDC

A

DCDC

B

PCDU Modules- Charge control

- Battery / Power Bus IF

- Pwr Bus Filter

- Power Distribution (LCL)

- Special. Actuation outlets

- Pwr Status / Monitoring

- DC/DC external supply

LCL, switches

SAR

(MPPT)

Battery

IF

PWR Bus

Filter

Launch your visions

Thank you very much for your attention.

Small Satellites Optical Instruments Satellite Equipment

spacetech gmbh€¦ · company presentation 12 formosat-5 primary structure, top panel, mgse...

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